基于多模型的低轨星座多目标跟踪传感器资源调度

针对低轨星座多目标持续跟踪传感器资源调度问题,首先将目标跟踪任务划分为高精度任务集合和低精度任务集合,并分析了跟踪任务状态转移过程;然后,为两任务集合分别建立了基于动态优先级的优化调度模型,提出了一种基于多模型的实时传感器调度算法。不同场景下仿真实验表明,所提算法较之以跟踪精度为优化目标和以跟踪精度为门限约束的方法具有更强的适用性,尤其对于目标分布较为集中的情况,其目标丢失率大大降低,尽管个别目标的跟踪误差略有增大。     

半模机翼振动的风洞实验技术研究

飞行器机模型振动是影响其风洞实验数据可靠性的主要因素之一。为此,通过专门研制的半模振动模型,采用对称翼型NACA0012和层流翼型NACA64-210两种半模机翼进行了低速风洞振动实验。选取五种激振方式,用直接测力法得到模型在静态和不同激振方式下升力特性变化曲线,研究了振动频率、自然转捩和固定转捩、数据采集方式等参数对机翼气动特性测量结果的影响。结果表明：振动对半模机翼气动特性的影响程度因不同翼型构型、不同采集方式和翼面不同流动模式等而产生不同效果。结论对提高飞机模型风洞实验大迎角振动情况下的测量精准度有参考价值。     

Properties of Ground Level Enhancement Events and the Associated Solar Eruptions During Solar Cycle 23

Solar cycle 23 witnessed the most complete set of observations of coronal mass ejections (CMEs) associated with the Ground Level Enhancement (GLE) events. We present an overview of the observed properties of the GLEs and those of the two associated phenomena, viz., flares and CMEs, both being potential sources of particle acceleration. Although we do not find a striking correlation between the GLE intensity and the parameters of flares and CMEs, the solar eruptions are very intense involving X-class flares and extreme CME speeds (average ～2000?km/s). An M7.1 flare and a 1200?km/s CME are the weakest events in the list of 16 GLE events. Most (80?%) of the CMEs are full halos with the three non-halos having widths in the range 167 to 212?degrees. The active regions in which the GLE events originate are generally large: 1290?msh (median 1010?msh) compared to 934?msh (median: 790?msh) for SEP-producing active regions. For accurate estimation of the CME height at the time of metric type?II onset and GLE particle release, we estimated the initial acceleration of the CMEs using flare and CME observations. The initial acceleration of GLE-associated CMEs is much larger (by a factor of 2) than that of ordinary CMEs (2.3?km/s² vs. 1?km/s²). We confirmed the initial acceleration for two events for which CME measurements are available in the inner corona. The GLE particle release is delayed with respect to the onset of all electromagnetic signatures of the eruptions: type?II bursts, low frequency type?III bursts, soft X-ray flares and CMEs. The presence of metric type?II radio bursts some 17?min (median: 16?min; range: 3 to 48?min) before the GLE onset indicates shock formation well before the particle release. The release of GLE particles occurs when the CMEs reach an average height of ～3.09?R _s (median: 3.18?R _s ; range: 1.71 to 4.01?R _s ) for well-connected events (source longitude in the range W20–W90). For poorly connected events, the average CME height at GLE particle release is ～66?% larger (mean: 5.18?R _s ; median: 4.61?R _s ; range: 2.75–8.49?R _s ). The longitudinal dependence is consistent with shock accelerations because the shocks from poorly connected events need to expand more to cross the field lines connecting to an Earth observer. On the other hand, the CME height at metric type?II burst onset has no longitudinal dependence because electromagnetic signals do not require magnetic connectivity to the observer. For several events, the GLE particle release is very close to the time of first appearance of the CME in the coronagraphic field of view, so we independently confirmed the CME height at particle release. The CME height at metric type?II burst onset is in the narrow range 1.29 to 1.8?R _s , with mean and median values of 1.53 and 1.47?R _s . The CME heights at metric type?II burst onset and GLE particle release correspond to the minimum and maximum in the Alfvén speed profile. The increase in CME speed between these two heights suggests an increase in Alfvénic Mach number from?2 to?3. The CME heights at GLE particle release are in good agreement with those obtained from the velocity dispersion analysis (Reames in Astrophys. J. 693:812, 2009a; Astrophys. J. 706:844, 2009b) including the source longitude dependence. We also discuss the implications of the delay of GLE particle release with respect to complex type?III bursts by ～18?min (median: 16?in; range: 2 to 44?min) for the flare acceleration mechanism. A?similar analysis is also performed on the delay of particle release relative to the hard X-ray emission.     

Static aeroelastic analysis of very flexible wings based on non-planar vortex lattice method

A rapid and efficient method for static aeroelastic analysis of a flexible slender wing when considering the structural geometric nonlinearity has been developed in this paper. A non-planar vortex lattice method herein is used to compute the non-planar aerodynamics of flexible wings with large deformation. The finite element method is introduced for structural nonlinear statics analysis. The surface spline method is used for structure/aerodynamics coupling. The static aeroelastic characteristics of the wind tunnel model of a flexible wing are studied by the nonlinear method presented, and the nonlinear method is also evaluated by comparing the results with those obtained from two other methods and the wind tunnel test. The results indicate that the traditional linear method of static aeroelastic analysis is not applicable for cases with large deformation because it produces results that are not realistic. However, the nonlinear methodology, which involves combining the structure finite element method with the non-planar vortex lattice method, could be used to solve the aeroelastic deformation with considerable accuracy, which is in fair agreement with the test results. Moreover, the nonlinear finite element method could consider complex structures. The non-planar vortex lattice method has advantages in both the computational accuracy and efficiency. Consequently, the nonlinear method presented is suitable for the rapid and efficient analysis requirements of engineering practice. It could be used in the preliminary stage and also in the detailed stage of aircraft design.     

用FPGA实现abc坐标系的三维空间矢量调制算法

研究了一种应用于三相四桥臂逆变器的基于abc坐标系的新的空间矢量调制算法,避免了传统的αβ0坐标变换,使开关矢量的选取和占空比的计算更简单,显著降低了调制算法的复杂性。同时详细说明了基于abc坐标系的空间矢量脉宽调制算法的原理,并研究了用FPGA来实现该空间矢量调制算法的方法。由于FPGA不需要顺序执行指令,可以多个进程并发执行,响应速度快,可明显提高系统性能。仿真和实验结果证明了该空间矢量调制算法的正确性和利用FPGA实现该算法的可行性。     

面向小行星微重力环境探测的自恢复直立弹跳机器人设计

针对小行星微重力环境,提出了一种具有蛋形外壳,利用弹簧蓄力的并联腿弹跳机器人.该机器人无论以何种姿态落地,均可在重力矩作用下恢复直立姿态.这一设计相对于需要额外主动装置恢复直立的先前方案,节省了恢复直立所需的能耗,在结构上更为简单可靠.文中阐述了完整的机构设计方案,及相应的结构参数优化计算方法.通过的样机实验,设计方法...     

某型直升机尾上舱结构失稳故障研究

针对某型直升机尾上舱结构失稳故障,从直升机结构组成、故障现象入手,深入分析故障产生的原因,将结构修理中单一的割修、贴补和加强等方法,综合运用在结构失稳故障的排除中,从根本上杜绝类似的故障再发生,为直升机用户提供了一个更加安全可靠的机体结构平台。     

宽温域下三位四通电磁液动换向阀的几何尺寸链与卡滞特性

针对某型飞机服役环境中滑阀出现卡滞和动作延迟等现象,在分析滑阀机理的基础上,发现按常温设计的滑阀副配合间隙在服役环境下会发生较大变化,飞行器极端温度环境、精密偶件加工残余应力等容易造成滑阀卡滞。利用弹性力学和热变形理论,考虑残余应力的影响,推导了滑阀副径向尺寸链的数学表达式。以某型滑阀副为例,计算了-50℃、100℃和150℃下滑阀副的变形量,通径13mm的滑阀,径向尺寸最大变形量为2.9μm。采用有限元方法仿真分析了油液压力引起的阀套变形量,最大变形量为2.19μm。配合间隙最小值应不小于总变形量5.19μm,可近似取为5μm。计算了不同配合间隙时的内泄漏量,泄漏量应满足要求0.035L/min,对应的最大配合间隙为7.7μm,可近似取为8μm。本文所提出的分析方法和尺寸链计算模型,对滑阀设计具有一定的参考意义。     

月球重力场模型精度比较研究

从阶方差、谱域分析以及大地水准面自由空气重力异常3个方面分析了月球重力场模型LP150Q,LP165P与SGM150各自的特点及差异,研究结果表明,SGM150重力场在中高阶项上得到了明显改善,在远月面可以发现明显的重力异常正负交替的现象。另外,对"嫦娥二号"变轨试验期间的测轨数据进行了轨道解算和预报,比较不同重力场模型的精度影响,发现基于SGM150模型的解算结果优于基于LP150Q和LP165P的,在定轨弧段内有10m量级的精度提升,可用于高精度的月球探测器精密定轨。     

Diverse AdaBoost-SVM分类方法及其在航空发动机故障诊断中的应用

 提出采用考虑到精度/差异权衡的SVM作为弱分类器的一种新的组合分类诊断方法——Diverse AdaBoost-SVM。该方法通过在一组具有适当精度的弱分类器中进一步选择具有较大差异性的弱分类器,对这些具有较大差异性的弱分类器进行组合,从而较好解决AdaBoost算法中存在的精度/差异权衡的难题;同时该方法也较好地解决了现有的AdaBoost方法存在的弱分类器本身参数选取困难问题及训练轮数T的合理选取问题。通过对基准数据库的测试及航空发动机故障样本的诊断,结果表明和其他方法相比,Diverse AdaBoost -SVM方法具有更好的泛化性能,更适合对分散程度较大、聚类性较差的航空发动机故障样本进行分类,也更适合对非对称故障样本集进行分类。